US5306088A - Method and apparatus for monitoring the temperature in a turbine component - Google Patents

Method and apparatus for monitoring the temperature in a turbine component Download PDF

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Publication number
US5306088A
US5306088A US08/011,220 US1122093A US5306088A US 5306088 A US5306088 A US 5306088A US 1122093 A US1122093 A US 1122093A US 5306088 A US5306088 A US 5306088A
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Prior art keywords
fiber
bearing
optical cable
turbine
temperature
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Expired - Fee Related
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US08/011,220
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English (en)
Inventor
Walter Zoerner
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Siemens AG
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Siemens AG
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Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ZOERNER, WALTER
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K11/00—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00
    • G01K11/32—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using changes in transmittance, scattering or luminescence in optical fibres
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/12—Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load
    • F16C17/24—Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load with devices affected by abnormal or undesired positions, e.g. for preventing overheating, for safety
    • F16C17/243—Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load with devices affected by abnormal or undesired positions, e.g. for preventing overheating, for safety related to temperature and heat, e.g. for preventing overheating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/06—Sliding surface mainly made of metal
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2233/00—Monitoring condition, e.g. temperature, load, vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2360/00—Engines or pumps

Definitions

  • the invention relates to a method and an apparatus for monitoring the temperature in a turbine component, such as a turbine shaft bearing or a turbine blade.
  • German Patent DE-PS 21 36 809 discloses monitoring the temperature in a bearing with the aid of a thermocouple. However, only a local temperature increase in the bearing can be detected in that case. Detection of temperature over a large surface area in the bearing requires the use of a great number of thermocouples distributed over the bearing surface. That in turn means that there will be a number of measurement points and extensive cables and it is therefore especially complicated and expensive.
  • damage that leads to a lowering of efficiency of the turbine system can be caused by operationally-dictated factors.
  • Possible causes include not only the aforementioned overheating in a turbine bearing, but also the formation of a coating on the turbine blades, foreign bodies entrained by the operating medium, erosion, or an enlargement of a radial gap between adjacent guide blades and rotor blades.
  • damage could only be recognized indirectly, from a change in the efficiency.
  • Such changes are typically detected by measurements of the pressure and temperature of the operating medium at tapping points that are intended for other purposes.
  • the invention is based on the recognition that the index of refraction and thus the photoconduction properties in a fiber-optical cable vary in the region of a local temperature change.
  • a method for monitoring temperature in a turbine component which comprises detecting a change in photoconduction properties in a fiber-optical cable disposed inside a turbine component, being caused by a temperature change in the turbine component.
  • a method which comprises ascertaining the temperature change in the turbine component from a difference between light intensities at an inlet and at an outlet of the fiber-optical cable.
  • a method which comprises measuring the transit time of light reflected inside the fiber-optical cable, which is a function of the site of the temperature change.
  • an apparatus for monitoring temperature in a turbine component comprising a fiber-optical cable disposed in the interior of a turbine component, and means for detecting a change in photoconduction properties in the fiber-optical cable being caused by a temperature change in the turbine component.
  • the turbine component is a blade ring or a part of a blade ring, such as a turbine blade or a blade rim.
  • the fiber-optical cable is suitably disposed inside at least one guide blade of a guide blade ring. In that case, the equipment cost for measurement value processing is comparatively low, because in contrast to the rotating rotor blade ring, the guide blade ring is fixed.
  • the component is a turbine bearing
  • the fiber-optical cable is disposed just beneath the running surface of the bearing in a bearing shell made of bearing material, preferably white metal.
  • the fiber-optical cable is laid in an arbitrary form over an arbitrarily large portion of the bearing.
  • the fiber-optical cable is disposed in a meandering fashion over at least a portion of the bearing or bearing shell.
  • a plurality of fiber-optical cables are disposed in different planes of the bearing.
  • temperature detection that covers an especially large surface and thus ascertainment of the temperature profile of the entire bearing surface is attained.
  • a temperature profile that varies as a consequence of a malfunction can advantageously also be detected.
  • the fiber-optical cables may be disposed either inside or beneath the white metal layer.
  • the fiber-optical cable is laid in conduits in the bearing or inside the bearing shell.
  • conduits instead of conduits, grooves with coverings may also be provided. This reliably prevents the fiber-optical cable from being torn apart by locally varying thermal expansions in the bearing.
  • an optical directional coupler for outputting light reflected as a result of a temperature change inside the fiber-optical cable.
  • the light is fed in the form of light pulses.
  • a laser serving as the light source and being connected to an evaluation device such as a process computer.
  • a light-emitting diode (LED) may also be used as the light source.
  • the evaluation device is connected to the directional coupler, in order to ascertain the temperature profile inside the turbine component with the aid of the evaluation device.
  • the temperature profile inside the turbine component is ascertained from the intensities of the reflected light and of the light at the inlet and outlet of the fiber-optical cable, and from the transit time of the reflected light.
  • the temperature profile is displayed on a screen, preferably in three dimensions.
  • the advantages attained with the invention are in particular that for a comprehensive evaluation of the status of a turbine component, such as a turbine bearing or turbine blade, the temperature in the component can be monitored with only a single fiber-optical cable, thereby avoiding a great number of individual measurements.
  • the fiber-optical cable is disposed in a close-mesh network over the length of the component, making it possible to conclude that a change in temperature has occurred by way of an approximation of measured temperature courses. This makes it possible in turn to ascertain and display a temperature profile in terms of the quantity and direction of propagation of temperature changes.
  • Using the fiber-optical cable to monitor the temperature of a turbine blade moreover makes it possible to ascertain temperature changes in the operating medium in the various turbine stages. A change in the temperature of the operating medium in turn makes it possible, in a simple way, for an impending lowering of efficiency of a single involved turbine stage to be recognized early.
  • FIG. 1 is a simplified, partially diagrammatic and perspective and partially schematic view of an apparatus according to the invention with a fiber-optical cable in one bearing half of a turbine bearing;
  • FIG. 2 is a perspective view of the bearing half of FIG. 1, with a fiber-optical cable disposed inside a bearing shell;
  • FIG. 3 is a perspective view of the bearing half of FIG. 2, with a fiber-optical cable disposed below the bearing shell;
  • FIG. 4 is a diagrammatic and schematic view of the apparatus of FIG. 1, having a directional coupler
  • FIG. 5 is a diagrammatic and schematic view of the configuration according to FIG. 4, with two fiber-optical cables in a turbine bearing, that are disposed in grid-like fashion;
  • FIG. 6 is a fragmentary, elevational view of a configuration of a fiber-optical cable in a guide blade ring of a turbine stage.
  • FIG. 1 there is seen an apparatus 1 for monitoring temperature in a turbine bearing 2, of which only a lower bearing half 4 is shown.
  • the apparatus 1 includes a fiber-optical cable 8 disposed just underneath a running surface 6 of the bearing.
  • the fiber-optical cable 8 extends axially in a region of the greatest friction output, or in other words in a support region of the bearing 2.
  • the bearing 2 ma be a slide bearing of a turbine shaft.
  • the fiber-optical cable 8 has a diameter of approximately 0.2 mm and is surrounded by a non-illustrated outer sheath which, for instance, is made of a nickel alloy.
  • a short, intensive light pulse L having an intensity I is input into the fiber-optical cable 8 through an inlet E thereof with the aid of a laser 10.
  • Light L' supplied at an outlet A of the fiber-optical cable 8 is detected by a light sensor 12, such as a photodiode, and is converted into a corresponding electrical signal.
  • the light sensor 12 is part of an evaluation device 14, which is connected to the laser 10 through a line 16.
  • some other light source such as an LED, may also be provided.
  • the photoconduction properties in the fiber-optical cable 8 change. This causes scattering losses inside the fiber-optical cable 8 and therefore a change in intensity I' of the light L' at the outlet A. This change is transmitted through the light sensor 12 to the evaluation device 14. In the evaluation unit 14, the degree of the temperature change is ascertained from the difference between the respective intensities I and I' of the light at the inlet E and the outlet A of the fiber-optical cable 8.
  • At least part of the fiber-optical cable 8 is advantageously disposed in meandering fashion. Examples of such a configuration are shown in FIGS. 2 and 3.
  • the fiber-optical cable 8 is disposed inside a bearing shell 18 of white metal, which forms the running surface 6 of the bearing 2, to reduce the sliding friction. To that end, before the bearing is lined with white metal, the fiber-optical cable 8 is laid in a meandering fashion, or in the manner of a coil in the form of windings, on the inner surface of the bearing 2.
  • the fiber-optical cable 8 is suitably laid just beneath the bearing shell 18 formed of white metal, in conduits 20. Grooves which are provided with coverings after the fiber-optical cable 8 has been laid and before the white metal has been applied, may also be provided, instead of the conduits 20, in a manner that is not shown in detail.
  • FIG. 4 shows an apparatus 1 with an optical directional coupler 22 connected into the fiber-optical cable 8.
  • an optical directional coupler 22 Through the use of the optical directional coupler 22, light L" which is reflected in the fiber-optical cable as a result of a temperature change inside the bearing 2, is output and transmitted, optionally through an optical amplifier 24, by means of a fiber-optical cable 26 to the evaluation device 14. There, the site of the temperature change inside the bearing 2 is ascertained from the measurement of the transit time of the reflected light L" which has an intensity I".
  • the fiber-optical cable is split into two branches 8a and 8b, which are disposed in gridlike fashion in two planes in the bearing half 4 of the bearing 2. Large-area temperature monitoring is accordingly achieved.
  • Each branch 8a and 8b includes one respective directional coupler 22a and 22b and these are each connected to the evaluation device 14 through a respective fiber-optical cable 26a and 26b.
  • the temperature profile in the bearing 2 is ascertained from the intensities I, I' and I" and the transit time of the reflected light L", for instance by means of a computer, and is displayed on a non-illustrated screen in two or three dimensions.
  • the temperature distribution over the running surface 6 of the bearing 2 is integrally detected, assuring a comprehensive evaluation of the status of the bearing.
  • the measurement accuracy along one meter of the fiber-optical cable is approximately 1° C.
  • FIG. 6 shows one half of a guide blade ring 30 having a number of guide blades 31.
  • the guide blade ring 30 is part of a turbine stage, for instance a low-pressure stage of a steam turbine.
  • the guide blade ring 30 includes respective outer and inner blade rims 33 and 34 and the guide blades 31 are secured in these rims.
  • a fiber-optical cable 8' is preferably disposed inside non-illustrated conduits, which extend radially through the guide blades 31.
  • the fiber-optical cable 8' is located inside the outer and inner blade rims 33 and 34 at respective turning points 35 and 36.
  • fiber-optical cables in turbine system parts, such as in the leading and trailing portions of turbine housings, in the condensor, or in a heat exchanger on the steam and water side, makes it possible to monitor the steam or condensate temperatures indirectly.
  • the fiber-optical cable is often disposed on or in a separate carrier.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Radiation Pyrometers (AREA)
  • Measuring Temperature Or Quantity Of Heat (AREA)
US08/011,220 1992-01-29 1993-01-29 Method and apparatus for monitoring the temperature in a turbine component Expired - Fee Related US5306088A (en)

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Application Number Priority Date Filing Date Title
DE4202440 1992-01-29
DE4202440 1992-01-29

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Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0806642A1 (de) * 1996-05-09 1997-11-12 DaimlerChrysler Aerospace Airbus Gesellschaft mit beschränkter Haftung Verfahren und Anordnung zur Temperaturerfassung in Räumen, insbesondere in Passagier- oder Frachträumen in Flugzeugen
WO1998026336A1 (en) * 1996-12-13 1998-06-18 Siemens Corporate Research, Inc. A method for blade temperature estimation in a steam turbine
US5838588A (en) * 1996-12-13 1998-11-17 Siemens Corporate Research, Inc. Graphical user interface system for steam turbine operating conditions
US6079875A (en) * 1997-09-04 2000-06-27 Alcatel Apparatus for measuring the temperature of an object with a temperature sensor and method of making the temperature sensor
US6305427B1 (en) 1999-11-19 2001-10-23 Kenway Corporation Double walled apparatus and methods
US20020122458A1 (en) * 2000-12-28 2002-09-05 Ingallinera Michael David Utilization of pyrometer data to detect oxidation
US20020125414A1 (en) * 2001-03-10 2002-09-12 Hans-Joachim Dammann Method using an optical signal for detecting overheating and fire conditions in an aircraft
US6513971B2 (en) * 2000-11-30 2003-02-04 Rolls-Royce Plc Heatable member and temperature monitor therefor
US6595684B1 (en) 1999-11-03 2003-07-22 Northrop Grumman Corporation System and method for evaluating a structure
US20050013342A1 (en) * 2003-07-17 2005-01-20 Kaminski Christopher Anthony Measuring temperature in stationary components of electrical machines using fiber optics
US20050129088A1 (en) * 2003-12-11 2005-06-16 Rajendran Veera P. Methods and apparatus for temperature measurement and control in electromagnetic coils
WO2005093221A1 (de) * 2004-03-23 2005-10-06 Siemens Aktiengesellschaft Anordnung und verfahren zur beschädigungsdetektion an einer komponente einer strömungsmaschine
EP1591627A1 (de) * 2004-04-27 2005-11-02 Siemens Aktiengesellschaft Regeleinrichtung für einen Kompressor sowie Verwendung eines Bragg-Gitter-Sensors bei einer Regeleinrichtung
EP1804056A2 (de) 2003-06-30 2007-07-04 Siemens Power Generation, Inc. Verfahren und Vorrichtung zur Online-Messung von Defekten bei Turbinenwärmedämmschichten
US20070223557A1 (en) * 2005-12-07 2007-09-27 Pavel Pevzner Method and system for detecting damage in layered structures
US20070258807A1 (en) * 2006-05-04 2007-11-08 Siemens Power Generation, Inc. Infrared-based method and apparatus for online detection of cracks in steam turbine components
US20110026872A1 (en) * 2007-11-29 2011-02-03 Martin Vincent Davies Device for applying a fiber-optic monitoring system to a component to be monitored
US20170089806A1 (en) * 2015-09-30 2017-03-30 Deere & Company Methods to determine a bearing setting
US20190186283A1 (en) * 2017-12-18 2019-06-20 Rolls-Royce North American Technologies Inc. Apparatus and method for measuring turbine temperature
US10871403B1 (en) 2019-09-23 2020-12-22 Kidde Technologies, Inc. Aircraft temperature sensor

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JPH07113833A (ja) * 1993-10-20 1995-05-02 Power Reactor & Nuclear Fuel Dev Corp 導体接続部の異常検出装置
WO2009149971A1 (de) * 2008-06-12 2009-12-17 Siemens Aktiengesellschaft Lagerschale für ein gleitlager sowie vorrichtung und verfahren zum ortsaufgelösten ermitteln der temperatur einer lagerschale in einem gleitlager
DE102009039259B4 (de) * 2009-08-28 2016-07-28 Sms Group Gmbh Überwachung von Walzenlagern

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EP0023345A2 (de) * 1979-07-30 1981-02-04 Kabushiki Kaisha Toshiba Optisches Messgerät
US4408827A (en) * 1981-09-02 1983-10-11 United Technologies Corporation Imaging system for hostile environment optical probe
US4525626A (en) * 1982-03-24 1985-06-25 Sperry Corporation Fiber optic vibration modal sensor
US4545253A (en) * 1983-08-29 1985-10-08 Exxon Production Research Co. Fiber optical modulator and data multiplexer
US4823166A (en) * 1985-08-20 1989-04-18 York Limited Optical time-domain reflectometry
US4734577A (en) * 1986-01-30 1988-03-29 Grumman Aerospace Corporation Continuous strain measurement along a span
JPS6378031A (ja) * 1986-09-22 1988-04-08 Mitsubishi Rayon Co Ltd 光温度センサ
DE3811824A1 (de) * 1987-04-10 1988-10-27 Vaisala Oy Verfahren zur faseroptischen temperaturmessung sowie vorrichtung hierfuer
DE3742331A1 (de) * 1987-12-14 1989-06-29 Hartmut Dr Gruhl Verfahren zur beeinflussung der leiteigenschaften von lichtwellenleitern in abhaengigkeit von der temperatur
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US4950886A (en) * 1989-06-30 1990-08-21 Claus Richard O Partially reflecting optical fiber splice for temperature and strain measurement
US5195359A (en) * 1989-07-18 1993-03-23 Nippon Mining Co., Ltd. Apparatus for detecting operating condition of internal-combustion engine
EP0421967A1 (de) * 1989-10-02 1991-04-10 Telefonaktiebolaget L M Ericsson Lichtleitfaser für die Detektion von Temperaturänderung

Cited By (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0806642A1 (de) * 1996-05-09 1997-11-12 DaimlerChrysler Aerospace Airbus Gesellschaft mit beschränkter Haftung Verfahren und Anordnung zur Temperaturerfassung in Räumen, insbesondere in Passagier- oder Frachträumen in Flugzeugen
WO1998026336A1 (en) * 1996-12-13 1998-06-18 Siemens Corporate Research, Inc. A method for blade temperature estimation in a steam turbine
US5832421A (en) * 1996-12-13 1998-11-03 Siemens Corporate Research, Inc. Method for blade temperature estimation in a steam turbine
US5838588A (en) * 1996-12-13 1998-11-17 Siemens Corporate Research, Inc. Graphical user interface system for steam turbine operating conditions
CZ300956B6 (cs) * 1996-12-13 2009-09-23 Siemens Corporate Research, Inc. Zpusob urcování teploty lopatek u parní turbíny
US6079875A (en) * 1997-09-04 2000-06-27 Alcatel Apparatus for measuring the temperature of an object with a temperature sensor and method of making the temperature sensor
US6595684B1 (en) 1999-11-03 2003-07-22 Northrop Grumman Corporation System and method for evaluating a structure
US6305427B1 (en) 1999-11-19 2001-10-23 Kenway Corporation Double walled apparatus and methods
US20090312956A1 (en) * 1999-12-22 2009-12-17 Zombo Paul J Method and apparatus for measuring on-line failure of turbine thermal barrier coatings
US7690840B2 (en) 1999-12-22 2010-04-06 Siemens Energy, Inc. Method and apparatus for measuring on-line failure of turbine thermal barrier coatings
US6513971B2 (en) * 2000-11-30 2003-02-04 Rolls-Royce Plc Heatable member and temperature monitor therefor
US6579005B2 (en) * 2000-12-28 2003-06-17 General Electric Company Utilization of pyrometer data to detect oxidation
US20020122458A1 (en) * 2000-12-28 2002-09-05 Ingallinera Michael David Utilization of pyrometer data to detect oxidation
US6881948B2 (en) * 2001-03-10 2005-04-19 Airbus Deutschland Gmbh Method using an optical signal for detecting overheating and fire conditions in an aircraft
US20050089081A1 (en) * 2001-03-10 2005-04-28 Hans-Joachim Dammann System for monitoring a temperature condition
US6960019B2 (en) * 2001-03-10 2005-11-01 Airbus Deutschland Gmbh Fiber optic temperature monitoring method
US20020125414A1 (en) * 2001-03-10 2002-09-12 Hans-Joachim Dammann Method using an optical signal for detecting overheating and fire conditions in an aircraft
US6945692B2 (en) * 2001-03-10 2005-09-20 Airbus Deutschland Gmbh Fiber optic temperature monitoring system
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